CN106662324B - Fuel nozzle body - Google Patents
Fuel nozzle body Download PDFInfo
- Publication number
- CN106662324B CN106662324B CN201580031080.XA CN201580031080A CN106662324B CN 106662324 B CN106662324 B CN 106662324B CN 201580031080 A CN201580031080 A CN 201580031080A CN 106662324 B CN106662324 B CN 106662324B
- Authority
- CN
- China
- Prior art keywords
- nozzle body
- fuel nozzle
- inner tube
- auxiliary section
- fuel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/36—Supply of different fuels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
- F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/40—Control of fuel supply specially adapted to the use of a special fuel or a plurality of fuels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2211/00—Thermal dilatation prevention or compensation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The present invention relates to a kind of fuel nozzle bodies (1) with rear end (2) and front end (3), the fuel nozzle body includes the inner tube (7) for extending to the outer tube (4) of the front end (3) from the rear end (2) and being concentrically disposed with the outer tube (4), the outer tube has the radial opening (5) for the first fuel (6) in the region of the front end (3), said inner tube is passed through in nozzle head (8) in the region of the front end (3), the nozzle head has the other opening (9) for the second fuel (10), wherein in the region of the front end (3), said inner tube (7) passes through two auxiliary sections (11, 12) guidance in the outer tube (4), described two auxiliary sections be arranged in the axial direction the radial opening (5) and it is described in addition Opening (9) between, and wherein, first auxiliary section (11) nearest from the radial opening (5) is configured to the connection sheet (13) around said inner tube (7), and wherein second auxiliary section (12) constitutes on ring week and has at least one discontinuities.Furthermore the present invention relates to a kind of burner (23) and a kind of gas turbines (24).
Description
Technical field
The present invention relates to a kind of fuel nozzle body, particularly for gas turbine burner fuel nozzle body, and relate to
And the compensation of thermal expansion.The present invention additionally relates to a kind of burner and a kind of gas turbine.
Background technique
Fuel nozzle or fuel nozzle body for gas operation and oil operation bear different temperature according to operation type,
Thus the measure for carrying out thermal compensation is needed.One such measure is that corrugated expansion joint is placed in position appropriate
Place, this usually cannot achieve due to space reasons and is relatively expensive if still disposing.
Summary of the invention
Therefore the object of the present invention is to a kind of fuel nozzle body be proposed, wherein solving the problems, such as thermal compensation at low cost.This
Other purposes of invention are to propose a kind of corresponding burner or corresponding gas turbine.
For fuel nozzle body purpose by proposing that a kind of fuel nozzle body according to the present invention is realized.About combustion
The purpose of burner is by proposing that a kind of burner according to the present invention is realized.Purpose about gas turbine is by proposing one
Kind gas turbine according to the present invention is realized.Dependent claims include advantageous design scheme of the invention.
According to the present invention, the fuel nozzle body with rear end and front end includes front end is extended to from rear end outer
There is the radial direction for the first fuel to open in the region of front end for pipe and the inner tube with outer concentric tube being arranged, the outer tube
Mouthful, said inner tube is passed through in nozzle head in the region of front end, and the nozzle head has other openings for the second fuel,
Wherein in the region of front end, inner tube is guided in outer tube by two auxiliary sections, and described two auxiliary sections are axially arranged
Between radial opening and other openings.
Therefore fuel nozzle body constitutes the compensating unit for having self-regulation.Inner tube is movably mounted in outer tube and designs
For so that said inner tube can compensate for the maximum thermal expansion of the two systems, it is logical that the outer tube and inner tube are formed together annular
Road.
Creative fuel nozzle body is characterized in that two auxiliary sections.
First auxiliary section nearest from radial opening is configured to the connection sheet around inner tube.The shape is simple and effective
's.
In order to which the fuel passed through at the first auxiliary section to be output in combustion chamber, the second auxiliary section is according to the present invention
Constituting on ring week has at least one discontinuities, i.e., for example constitutes with star, so that the second auxiliary section is not pasted on entire ring week
It leans against on the inside of outer tube, but is only sticked in some sections upper on the inside of outer tube or be similar to the first auxiliary section as circular
, but with discontinuities connection sheet.In allowing open region, " leaked fuel " can be safely in the second auxiliary section
Side flows through and into combustion chamber.
In an advantageous embodiment of the invention, the first auxiliary section has tightened up compared with the second auxiliary section
Cooperation requires.Particularly, it for the first auxiliary section (also referred to as leakage auxiliary section), defines relative to the second auxiliary section more
Big gap, however there is closer cooperation, therefore the gap allows relatively large leakage (such as about existing injection
Hole realizes the dissipation on all syringes only < 1% up to 5%).Therefore can guarantee to mix gas/air
The influence as small as possible of object.
In another advantageous embodiment, the second auxiliary section has narrower gap compared with the first auxiliary section.Second
Narrower gap in auxiliary section causes: avoiding being expected in other cases in the region that the first auxiliary section leaks auxiliary section
Abrasion.Thus the leakage cooperation of lasting stability as far as possible is ensured on the whole service duration, mode is: first matches
Conjunction portion contacts always to realize annular gap in no instance with outer tube.
In order to guide the two pipes persistently in another for most preferably one, it is also advantageous that, the second cooperation
Portion is chromium plating.
It, can be advantageously, the second auxiliary section be hardening, so that the second auxiliary section is at its surface as alternative
There is higher hardness compared with its host material.
About nozzle head advantageously, the nozzle head and inner tube are detachably connected.This permission when carrying out maintenance work
Simpler and more inexpensive replacement.
In an advantageous embodiment, inner tube is stretched out in the region of front end from outer tube and in inner tube from outer
Circular connection sheet is provided on the part that pipe stretches out.
The connection sheet can be used as the supporting part for nozzle head.
But as alternative, this connection sheet also can with sleeve combination be used as the anti-lost dress for inner tube
Set, the sleeve it is detachably connected with the front end of outer tube on its first end and on its second end by means of diameter
The circular connection sheet of inner tube is engaged to inwardly directed edge from rear.
Herein appropriately, sleeve optimization is fluidly constituted.
Preferably, inner tube is oil pipe line and is used to supply nozzle head.
It is furthermore preferred that being gas piping by the circular passage that inner and outer tubes are formed.
Burner according to the present invention is equipped with fuel nozzle body according to the present invention, and the burner is more particularly to being combustion
Gas-turbine burner.
Advantageously, having compressor, turbine and the gas turbine of combustion chamber includes this burner.
Detailed description of the invention
Other feature of the invention, characteristics and advantages are obtained from reference next to description of the attached drawing to embodiment.
Fig. 1 shows the schematic diagram of gas turbine,
Fig. 2 shows the view of atomizer burner,
Fig. 3 shows the fuel nozzle body with oil and gas jetting device according to prior art, the oil and gas spray
Enter device and do not have thermal compensation function,
Fig. 4 shows the fuel nozzle body with oil and gas jetting device according to the present invention, and the oil and gas spray into
Device has thermal compensation function,
Fig. 5 shows the three-dimensional view of the inner tube in the region of front end,
Fig. 6 shows the section of the inner tube in the region of front end,
Fig. 7 shows the section of the outer tube in the region of front end,
Fig. 8 shows the three-dimensional view of the front end of fuel nozzle body,
Fig. 9 shows the section of the front end of fuel nozzle body, and
Figure 10 shows the front end of the fuel nozzle body with stop sleeve.
Specific embodiment
Fig. 1 schematically shows gas turbine 31.The gas turbine includes compressor section 32, combustor section 33 and whirlpool
Section 34 and combustion chamber 27 are taken turns, the combustion chamber has at least one burner 23 in the region of combustor section 33.?
This burner 23 is described in detail in Fig. 2.Burner 23 has fuel nozzle body 1, and the fuel nozzle body is in Fig. 3 to 10
Detailed description.
When gas turbine 31 is run, air is inhaled by the air intake of compressor section 32 and is pressed at this
Contracting.Compressed air is fed to combustion chamber 27, and the combustion chamber is arranged in combustor section 33.Gaseous or liquid
Fuel, such as gas or oil, be also injected into combustion chamber 27 via burner 23 or fuel nozzle.Here, fuel nozzle
Body includes fuel nozzle/opening of for liquid and gaseous fuel.Generated air/fuel mixture be ignited and
It burns in combustion chamber 27.The burning waste gas of heat is flowed into turbine section 34 from combustor section 33, burning at this
Waste expansion and cooling.
Fig. 2 schematically and is exemplarily illustrated burner 23, outstanding in the section with so-called nozzle carrier 35
Its atomizer burner.Nozzle carrier 35 includes that the hot side 37 at runtime towards combustion zone 36 deviates from combustion zone 36 with opposite
Cold side 38, wherein the pre-mix tube 30 in nozzle carrier 35 extends to hot side 37 from cold side 38, that is, is parallel to burner 23
Main shaft 39 extends, and is respectively provided with the entrance 28 to premixing pipeline on cold side 38 and the outlet 40 in hot side 37.
Pre-mix tube 30 is used as jet nozzle, the jet nozzle be arranged in the present example two circles it is upper and
Fuel nozzle body 1 is provided at its entrance 28.At runtime, fuel 6,10 and compressor air 29 flow through jet stream spray
Mouth, i.e. pre-mix tube 30, and enter at the outlet of jet nozzle 40 as fuel-air mixture and limited by outer cover 41
In the combustion chamber 27 on boundary.
Fig. 3 is schematically and being exemplarily illustrated, there is the fuel of oil and gas jetting device according to prior art to spray
Mouth body 42.Fuel nozzle body 42 has rear end 2 and front end 3, and the rear end is for delivering fuel to fuel nozzle body
42, the front end has and the associated opening 5,9 of different fuel.Particularly, fuel nozzle body 42 includes from rear end 2
Extend to the outer tube 4 of front end 3 and the inner tube 7 including being concentrically disposed with outer tube 4, region of the outer tube in front end 3
In there is radial opening 5 for the first fuel 6, said inner tube is passed through in nozzle head 8 in the region of front end 3, described
Nozzle head has the other opening 9 for the second fuel 10.Fuel nozzle head 42 is arranged at the entrance 28 of premixing pipeline.
At runtime, compressed air 29 is passed through by fuel nozzle body 42 and is flowed into pre-mix tube 30.In gas operation,
Gaseous fuel 6 is guided through circular passage 21 and is injected to the sky around fuel nozzle body 42 via radial opening 5
In air-flow 29, the circular passage passes through inner tube 7 and the formation of outer tube 4.In oil operation, oil conveying is via inner tube 7 and nozzle head 8
It carries out.The nozzle head has the other opening 9 for being injected to oil 10 in circular air stream 29.Annular is logical as a result,
The effect of road 21 is gas piping 22 and the effect of inner tube 7 is oil pipe line 20.
Fig. 4 shows the fuel nozzle body 1 according to the present invention with thermal compensation function, and the thermal compensation function passes through as follows
Mode is realized, i.e., in the region of front end 3, inner tube 7 is guided in outer tube 4 by two auxiliary sections 11,12, the auxiliary section
It is arranged between radial opening 5 and other opening 9 in the axial direction.
Figures 5 and 6 show three-dimensional view and section of the inner tube 7 in the region of front end 3.It can see the first auxiliary section
11, the second auxiliary section 12 and circular connection sheet 15.Fig. 7 is shown " mating member ", that is, there is the radial direction for the first fuel 6 to open
The outer tube 4 of mouth 5.
Fig. 8 and 9 shows the three-dimensional view and section of the front end 3 of fuel nozzle body 1.
Outer tube 4, the connection sheet 15 of inner tube 7 and nozzle head 8 can be substantially seen in fig. 8, and the nozzle head, which has, to be used for
The other opening 9 of other fuel 10.
In fig. 9 it can be seen that nozzle head 8 and inner tube 7 are detachably connected, in shown example, nozzle head with
Inner tube is (referring to the spire 24) screwed.The clearance sealing component 14 of first auxiliary section 11 is configured to, so that leaking at runtime
Minimally, it controllably carries out.In particular, spraying into leakage of the region realization less than 5% about entire via the first auxiliary section 11.
Second auxiliary section 12 is designed as, so that second auxiliary section all ensures that more compared with the first auxiliary section 11 in any loading condition
Closely cooperation, also referred to as leakage cooperation, contacts to not generate the first auxiliary section 11 with any of the inside of outer tube 4, so that
Leakage is limited via the first auxiliary section 11.Particularly, compared with the first auxiliary section 11, the tolerance of the second auxiliary section 12 is tighter
Regulation.In order to make it work, auxiliary section 12 does not allow as auxiliary section 11 as circular connection sheet 13 around entire ring
Week reclines.For this reason, the second auxiliary section 12 constitutes (invisible in the cross-sectional view of Fig. 9, but Figure 10's with star
It is visible in embodiment).
Furthermore in fig. 9 it can be seen that in the region of front end 3, inner tube 7 is stretched out from outer tube 4.It can also be in fig. 8
See the circular connection sheet 15 on the part stretched out in the slave outer tube 4 for be arranged in inner tube 7.The connection sheet 15 can be used as with
In the supporting member of nozzle head 8.Fig. 9 shows the expansion path 25 between the front end and connection sheet 15 of outer tube 4.
Figure 10 shows the application of the alternative for connection sheet 15.Here, sleeve 16 on its first end 17 with outer tube 4
Front end 3 is detachably connected, such as screws.On its second end 18, sleeve 16 is by means of the edge that is oriented radially inwards
19 engage the circular connection sheet 15 of inner tube 7 from rear.Sleeve 16 should prevent inner tube 7 from losing.Furthermore Figure 10 is shown: sleeve 16 is excellent
Change fluidly constitute and it is tapered towards front end 3.
Claims (13)
1. one kind has the fuel nozzle body (1) of rear end (2) and front end (3), the fuel nozzle body includes after described
The inner tube (7) that end (2) extends to the outer tube (4) of the front end (3) and is concentrically disposed with the outer tube (4), it is described outer
Pipe has the radial opening (5) for the first fuel (6) in the region of the front end (3), and said inner tube is in the front end
It being passed through in the region in portion (3) in nozzle head (8), the nozzle head has the other opening (9) for the second fuel (10),
In in the region of the front end (3), said inner tube (7) is drawn in the outer tube (4) by two auxiliary sections (11,12)
It leads, described two auxiliary sections are arranged in the axial direction between the radial opening (5) and the other opening (9), feature
It is, first auxiliary section (11) nearest from the radial opening (5) is configured to the connection sheet (13) around said inner tube (7),
And wherein the second auxiliary section (12) are constituted on ring week at least one discontinuities.
2. fuel nozzle body (1) according to claim 1, wherein first auxiliary section (11) and second auxiliary section
(12) compared to tightened up cooperation requirement.
3. fuel nozzle body (1) according to any one of the preceding claims, wherein second auxiliary section (12) and institute
Stating the first auxiliary section (11) and comparing has narrower gap.
4. fuel nozzle body (1) according to claim 1 or 2, wherein second auxiliary section (12) is chromium plating.
5. fuel nozzle body (1) according to claim 1 or 2, wherein second auxiliary section (12) is hardening.
6. fuel nozzle body (1) according to claim 1 or 2, wherein the nozzle head (8) can be torn open with said inner tube (7)
It connects with unloading.
7. fuel nozzle body (1) according to claim 1 or 2, wherein in the region of the front end (3), it is described interior
It manages (7) to stretch out from the outer tube (4), and is provided on the part of said inner tube (7) stretched out from the outer tube (4)
Circular connection sheet (15).
8. fuel nozzle body (1) according to claim 7, middle sleeve (16) is at its first end (17) and described outer
The front end (3) of pipe (4) is removedly connected, and the edge at its second end (18) by means of being oriented radially inwards
(19) from the circular connection sheet (15) of rear engagement said inner tube (7).
9. fuel nozzle body (1) according to claim 8, wherein the sleeve (16) optimization is fluidly constituted.
10. fuel nozzle body (1) according to claim 1 or 2, wherein said inner tube (7) is oil pipe line (20).
11. fuel nozzle body (1) according to claim 1 or 2, wherein the annular formed by inner tube (7) and outer tube (4)
Channel (21) is gas piping (22).
12. a kind of burner (23), with fuel nozzle body according to any one of the preceding claims (1).
13. a kind of gas turbine (24) has with compressor (25), turbine (26) and combustion chamber (27), the combustion chamber
There is at least one burner (23) according to claim 12.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102014220689.8 | 2014-10-13 | ||
| DE102014220689.8A DE102014220689A1 (en) | 2014-10-13 | 2014-10-13 | Fuel nozzle body |
| PCT/EP2015/073283 WO2016058903A1 (en) | 2014-10-13 | 2015-10-08 | Fuel nozzle body |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106662324A CN106662324A (en) | 2017-05-10 |
| CN106662324B true CN106662324B (en) | 2019-03-19 |
Family
ID=54293231
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201580031080.XA Active CN106662324B (en) | 2014-10-13 | 2015-10-08 | Fuel nozzle body |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US10591165B2 (en) |
| EP (1) | EP3134681B1 (en) |
| CN (1) | CN106662324B (en) |
| CA (1) | CA2958974C (en) |
| DE (1) | DE102014220689A1 (en) |
| WO (1) | WO2016058903A1 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102017120370B4 (en) * | 2017-09-05 | 2019-06-06 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Burner head, burner system and method of operating the burner system |
| KR102583223B1 (en) | 2022-01-28 | 2023-09-25 | 두산에너빌리티 주식회사 | Nozzle for combustor, combustor, and gas turbine including the same |
Family Cites Families (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS61223418A (en) | 1985-03-28 | 1986-10-04 | Sumitomo Metal Ind Ltd | Burner device |
| DD249612A3 (en) | 1985-05-14 | 1987-09-16 | Stroemungsmasch Veb | LIQUID BURNER WITH STEAM PRESSURE SCREENING |
| EP0337141A1 (en) * | 1988-03-31 | 1989-10-18 | Siemens Aktiengesellschaft | Optical fiber feedthrough for optoelectronic modules and methods of its manufacturing |
| US5410884A (en) | 1992-10-19 | 1995-05-02 | Mitsubishi Jukogyo Kabushiki Kaisha | Combustor for gas turbines with diverging pilot nozzle cone |
| DE4326802A1 (en) * | 1993-08-10 | 1995-02-16 | Abb Management Ag | Fuel lance for liquid and / or gaseous fuels and process for their operation |
| GB9321505D0 (en) * | 1993-10-19 | 1993-12-08 | Europ Gas Turbines Ltd | Fuel injector |
| AU1995199A (en) * | 1997-10-10 | 1999-05-03 | Westinghouse Electric Corporation | Fuel nozzle assembly for a low nox combustor |
| JP2000039147A (en) * | 1998-07-21 | 2000-02-08 | Mitsubishi Heavy Ind Ltd | Pilot nozzle for combustor equipped with flexible joint |
| DE19905995A1 (en) * | 1999-02-15 | 2000-08-17 | Asea Brown Boveri | Injection lance or nozzle for liquid and gaseous fuel in combustion chamber is part of secondary or tertiary burner around which flows hot gas jet in main flow direction |
| US7290394B2 (en) * | 2002-11-21 | 2007-11-06 | Parker-Hannifin Corporation | Fuel injector flexible feed with moveable nozzle tip |
| CN200958753Y (en) | 2006-06-30 | 2007-10-10 | 浦炳良 | Oil jetting nozzle for furnace |
| EP1936276A1 (en) * | 2006-12-22 | 2008-06-25 | Siemens Aktiengesellschaft | Gas turbine burner |
| US20100319353A1 (en) * | 2009-06-18 | 2010-12-23 | John Charles Intile | Multiple Fuel Circuits for Syngas/NG DLN in a Premixed Nozzle |
| EP2400216B1 (en) * | 2010-06-23 | 2014-12-24 | Alstom Technology Ltd | Lance of a Reheat Burner |
| US9133767B2 (en) * | 2011-08-02 | 2015-09-15 | Siemens Energy, Inc | Fuel injecting assembly for gas turbine engine including cooling gap between supply structures |
| US8801428B2 (en) | 2011-10-04 | 2014-08-12 | General Electric Company | Combustor and method for supplying fuel to a combustor |
-
2014
- 2014-10-13 DE DE102014220689.8A patent/DE102014220689A1/en not_active Ceased
-
2015
- 2015-10-08 WO PCT/EP2015/073283 patent/WO2016058903A1/en active Application Filing
- 2015-10-08 CN CN201580031080.XA patent/CN106662324B/en active Active
- 2015-10-08 CA CA2958974A patent/CA2958974C/en active Active
- 2015-10-08 EP EP15778915.7A patent/EP3134681B1/en active Active
- 2015-10-08 US US15/503,993 patent/US10591165B2/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| WO2016058903A1 (en) | 2016-04-21 |
| EP3134681B1 (en) | 2018-03-07 |
| CA2958974A1 (en) | 2016-04-21 |
| US10591165B2 (en) | 2020-03-17 |
| CN106662324A (en) | 2017-05-10 |
| DE102014220689A1 (en) | 2016-04-14 |
| EP3134681A1 (en) | 2017-03-01 |
| US20170276370A1 (en) | 2017-09-28 |
| CA2958974C (en) | 2018-11-13 |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220906 Address after: Munich, Germany Patentee after: Siemens energy Global Ltd. Address before: Munich, Germany Patentee before: SIEMENS AG |